Fluid flow ducts

ABSTRACT

A fluid flow duct of a gas turbine engine, the duct being defined between a fan cowl and a centrebody and there being provided movable flexible members attached to the centrebody; each member being movable within the duct by fluid pressure between a first concave position and a second convex position for varying the cross-sectional flow area of the duct.

United States Patent 1 1 McMurtry 1 1 Oct. 21, 1975 15 FLUID FLOW DUCTS 2,147,031 2/1939 Hastings 1. 138/45 x 3,146.851 9/1964 Ludlow et a1 .1 138/37 X [75] mentor: Dav'd Emmi 3,288,371 11/1966 Broughton 1. 239/534 x England 3,375,842 4/1968 Reader 1311/37 x 3 1 3,460,577 8/1969 Weathers 138/42 X [73] Ass1gnee. figlllzgfygi izz 3,718,160 2 1973 Jardiner et a1. 1313/45 [22] Flled: 1973 Primary ExaminerRichard C. Queisser 1211 Appl. No; 352,921 Assistant Examiner-Daniel M1 Yosich Attorney, Agent, or FirmStevens Davis, Miller & [30] Foreign Application Priority Data Mosher Apr. 27 1972 United Kingdom 19605/72 [57] ABSTRACT [52] US. Cl .1 138/37; 60/226 R; 138/46;

239/265; 251/5 A f'luld flow duct of a gas turbme engme. the duct [51] Int z H 8053 N30; FUD 1/02 being defined between a fan cowl and a centrebody [58] pick] of Search 138/3142 45.46; and there being provided movable flexible members 60/226 137/6569; 251/305 239/265 attached to the centrebody; each member being mov able within the duct by fluid pressure between a first concave position and a second convex position for [56] References Cited varying the cross-sectional flow area of the duct UNITED STATES PATENTS 6 Claims, 5 Drawing Figures 1,873,138 8/1932 Mitchell 1. [38/46 X US. Patent 0a. 21, 1975 Sheet 1 of 3 3,913,626

US. Patent 0a. 21, 1975 Sheet 2 on 3,913,626

U.S. Patent Oct. 21, 1975 Sheet 3 013 3,913,626

QN \NNN T R L llllll FLUID FLOW DUCTS This invention relates to fluid flow ducts. It is sometimes desirable to alter the cross-sectional fluid flow area of a duct. For example, to match the operating characteristics of a ducted fan gas turbine engine to the flight envelope of an aircraft in which it is installed it is desirable to be able to alter the cross-sectional area of the nozzle at the downstream end of the duct. It is known to use inflatable elastic members to vary the flow area of a duct, but in prior proposals the members were stretched in their operative positions and thus subject to fatigue.

According to this invention, however, a fluid flow duct comprises at least one wall defining the duct, a flexible sheet material member attached to the wall and means for changing the shape of the member between a first convex position and a second concave position for varying the cross-sectional flow area of the duct, wherein in said concave position the member lies in a recess in said wall, and both positions constitute unstretched positions of the member.

The fluid flow duct may be a fan duct of a ducted fan gas turbine engine comprising a fan cowl defining aradially outer duct wall, a centerbody defining a radially inner duct wall, a member attached to the centerbody and means for changing the shape of the member between a first, convex position and a second, concave position.

Preferably in the convex position the member follows the general shape of the centerbody, and in the concave position the member adopts the shape of the recess.

The member is preferably made in a flexible material and the first and second positions correspond to natural unstretched states of the member.

There may be a plurality of members attached to the centerbody and disposed, some in the first position and some in the second position.

The ducted fan gas turbine engine may be of the variable pitch fan type, and the fan cowl, andone or more members attached to the centerbody may be so arranged that together they form a nozzle at one end of the duct.

The cross-sectional flow area of the nozzle may be altered according to the position of each of the members.

The nozzle may act as an intake when used with a variable pitch fan gas turbine engine operating in the reversed pitch mode.

A specific embodiment of the invention will now be described with reference to the accompanying drawings wherein:

FIG. 1 is a longitudinal section through a gas turbine engine, including the duct of the present invention,

FIG. 2 is a view on the line I-I of FIG. 1,

FIG. 3 is a view on the line 11-]! of FIG. 2,

FIG. 4 is an expanded detail of a section on the line III-Ill of FIG. 3, and

FIG. 5 is a longitudinal section through a spool valve, for controlling the supply of compressed fluid to the members.

Referring now to the Figures, in FIG. 1 there is shown a front fan gas turbine engine 11 comprising an outer fan cowl l2 spaced from a centerbody 13 by struts 14 to define a fan duct. The cowl encloses a variable pitch fan 15 and a core engine 16 which is drivingly connected to the fan and is situated within the centrebody.

Such an engine may be used as a propulsion unit for an aircraft. In operation, with the fan in the forward pitch position, air enters an intake at 17, is compressed by the fan and delivered past a flow splitter I8 which divides the flow into two streams. A first stream flows through the core engine 16 in which it is further compressed by an intermediate compressor 19 and by a high pressure compressor 21, before entering a combustion chamber 22, where it is mixed with fuel and burned. The products of combustion flow through the several stages of a turbine 23 drivingly connected to the fan and the intermediate and high pressure compressors by shafts (not shown), and are then exhausted via the nozzle 24.

The second stream, which provides the main propulsive force from the engine, is delivered to atmosphere via the duct 25 and the nozzle 20 defined by the downstream end of the fan cowl l2 and the centerbody 13.

Referring now to FIGS. 1, 2 and 3, six flexible sheet material members 26 are mounted on the centerbody and secured to it at their edges. Each member is made of fibre-reinforced sheet rubber so that it is flexible but substantially inelastic, and is capable of being moved by means later described, between two positions including a first position 27 (shown in full lines in FIG. 1) in which it follows the general shape of the centerbody, and a second position 28 (shown in dotted lines), in which it lies flush with and is received in a recess which in this embodiment is in the form of a depression 29 in the centerbody. It will be understood that the recess may be merely a hole in the centerbody. In each of the positions 27,28 the member is substantially unstretched from its natural state. This enables many movements of the member to be made between its two operating positions before the material from which it is made fatigues rendering it unserviceable. The contours of each recess in the centerbody are blended gradually into the centrebody, as at 37, to prevent large deflections of the member along its line of attachment to the centerbody. Attachment of the member to the centerbody, is shown in FIG. 4 and may be achieved by bonding the edge 38 of each member into a metal channel section 39, the channel section 39 having internal ribs 40 which co-operate with ribs 41 on the member for retention thereof. The member is connected to the centerbody by bolts 42. As illustrated, the edge 38 is bonded without sharp bends to prevent relatively high local stresses at the edge.

The members 26 have been described as being constructed from fibre-reinforced rubber, in an analogous manner to a pneumatic tire carcass, but it will be appreciated that synthetic material or a sheet of metal could be used. In the case of a piece of sheet metal being used for the member 26 it would be formed by a pressing operation to produce, for example, the shape of the member in the convex position. In operation the edge of the member is rigidly clamped by bolts 42. A force is applied perpendicular to the convex surface so that the sheet inverts into the concave position. The concave position is the mirror image of the convex position so that both positions correspond to natural unstretched positions of the member.

For the conditions encountered during take off of an aircraft in which the gas turbine engine described above is installed, it is desirable to have the maximum nozzle area available, and thus at take-off all six members would lie in the second position 28. As the forward speed of the aircraft increases, the nozzle area required progressively decreases and this may be achieved by applying pressurized air to the underside of each of the members 26 in turn so as to move sequentially each member to the first position 27. It is preferable to have at least six members otherwise the sudden decrease in nozzle area as each member is sequentially moved to the first position may cause too sudden a pressure change in the duct 25 resulting in surging of the engine.

At cruise conditions the nozzle area required will be at a minimum and thus all six members will be in the first position 27.

For landing of the aircraft it is desirable to reverse the direction of thrust from the engines to achieve a braking effect. For this the pitch of the fan blades is reversed and the nozzle 20 of the duct 25 must act as the intake 31 to the fan, and a larger cross-sectional flow area is required than for the cruise condition. The large flow area is achieved by moving the members 26 se quentially back to the second position 28 as the forward speed of the aircraft falls prior to landing.

The members 26 are moved between the first and second positions by establishing a pressure differential across them. This is conveniently done using pressurized air from a compressor of the engine under the control of a spool valve 32 as shown in FIG. 5.

As the forward speed of the aircraft increases the Rayleigh pitot pressure, as sensed by a pilot tube 33, increases and this pressure is communicated to a resilient bellows 34 connected to the spool valve 32. Thus the degree of expansion of the bellows is proportional to the forward speed of the aircraft and the movement of the spool valve may be used sequentially to connect a source of relatively high pressure air 35, for example bleed air from the LP. (intermediate pressure )compressor 19, to galleries 36, each gallery connecting with one of the depressions 29 in the centrebody.

When the forward speed of the aircraft, and hence the pitot pressure, falls the spool valve 32 moves to the left and resets itself as the resilient bellows 34 recover their natural shape. A second spool valve, not shown but otherwise identical to the first spool valve, working in reverse may be used sequentially to vent the pressure in each of the galleries 36. The duct pressure will be sufficiently high to move each member 26 to the second position 28 once each gallery 36 has been vented.

[t is preferable that for use in a gas turbine engine the members are attached to the centrebody rather than to the fan cowl, as attachment to the fan cowl could result in a performance penalty due to increased base drag. It will however, be understood that in other applications of the invention for varying the flow area ofa duct there may be no objection to attaching the members to the radially outer duct wall, indeed in some applications there may of course be no centerbody or its equivalent.

I claim:

1. A fluid flow duct comprising at least one central wall defining the duct and for which there is provided a plurality of flow area varying means on said central wall therein, said flow area varying means each comprising one flexible sheet material flow area varying member, means for attaching said flow area varying members by their edges to the periphery of respective recesses in the central wall, said members being deployable in operation in either of two positions including a first concave position in which said members are received in the respective recesses and a second convex position, said members being substantially unstretched in either of said two positions, said second convex position being the mirror image of the first concave position and selectively varying the flow area through the duct, the separate fluid pressure means operable on said members for changing the position of said members between said first and second positions wherein fatigue in the unstretched members is substantially re duced.

2. A fluid flow duct according to claim 1 wherein said edges are attached to the respective recesses without sharp bends at said edges to prevent relatively high local stresses at said edges.

3. A fluid flow duct according to claim 1 in which said member is made from a fibre-reinforced rubber material.

4. A fluid flow duct according to claim I in which said member comprises a sheet metal pressing.

5. A fluid flow duct according to claim 1 in which the separate means for changing the position of said members comprise means for creating a pressure differential across the members.

6. A fluid flow duct according to claim 1 further comprising a plurality of flexible sheet material flow area varying members, each said member being attached by their edges to the periphery of a respective recess in the duct wall and wherein said pressure differential creating means includes means for creating the pressure differential across each member.

t =l t 

1. A fluid flow duct comprising at least one central wall defining the duct and for which there is provided a plurality of flow area varying means on said central wall therein, said flow area varying means each comprising one flexible sheet material flow area varying member, means for attaching said flow area varying members by their edges to the periphery of respective recesses in the central wall, said members being deployable in operation in either of two positions including a first concave position in which said members are received in the respective recesses and a second convex position, said members being substantially unstretched in either of said two positions, said second convex position being the mirror image of the first concave position and selectively varying the flow area through the duct, the separate fluid pressure means operable on said members for changing the position of said members between said first and second positions wherein fatigue in the unstretched members is substantially reduced.
 2. A fluid flow duct according to claim 1 wherein said edges are attached to the respective recesses without sharp bends at said edges to prevent relatively high local stresses at said edges.
 3. A fluid flow duct according to claim 1 in which said member is made from a fibre-reinforced rubber material.
 4. A fluid flow duct according to claim 1 in which said member comprises a sheet metal pressing.
 5. A fluid flow duct according to claim 1 in which the separate means for changing the position of said members comprise means for creating a pressure differential across the members.
 6. A fluid flow duct according to claim 1 further comprising a plurality of flexible sheet material flow area varying members, each said member being attached by their edges to the periphery of a respective recess in the duct wall and wherein said pressure differential creating means includes means for creating the pressure differential across each member. 